Payload recovery system



March 26, 1968 R. 1.. RODGER PAYLOAD RECOVERY SYSTEM 2 Sheets-Shem 1Filed March 16, 1966 o W m Tn m. V mmfim March 26, 1968 R. RODGERPAYLOAD RECOVERY SYSTEM 2 Sheets-Sheet 2 Filed March 16, 1966 INVENTORQOBEQT L. RODS R a A a.

3,374,739 Patented Mar. 26, 1968 fiFice United States Patet 3,374,739PAYLOAD RECOVERY SYSTEM Robert L. Rodger, Hackettstown, N.J., assignorto the United Statesof. America as represented by the Secretary of theArmy Filed Mar. 16, 1966,.Ser. No. 536,587 4Cla ims. (Cl. 102-56)ABSTRACT OF THE DISCLOSURE The invention described herein may bemanufactured and used by or for the Government for governmental purposeswithout the payment to me of any royalty thereon.

The invention relates to a projectile recovery system and moreparticularly to' a projectile recovery system utilizing a ballutedevice.

Since the advent of artillery, a nee-d to recover launched vehicles in asuitable manner has existed. The major consideration in recoveringlaunched vehicles or projectiles has been to provide a means of recoveryin a manner that allowsrelatively low deceleration loads upon impact. A

In the past, recovery was accomplished by one of three methods:

(1)"Have the vehicle launched in a parallel plane so that impact occursin a soft medium, water or on a rocket sled.

(2) Have the vehicle, in the .case of an artillery. projectile impactbase, launched from a vertical launching into a soft medium.

(3) Utilize a parachute to retard fall rate.

These aforementioned methods have proved unsatisfactory for thefollowing reasons:

(1) Depending upon a soft impact generates too high a g level.

(2) Catching the vehicle on a rocket sled is too expensive.

3) Utilizing a parachute encompasses too many types of failure, i.e.,shroud line entanglement, parachute collapsing, etc.

The novel drag device is devoid of the aforementioned deficiencies. Itis attached to and launched with the vehicle. Once it is inflated, thepossibility of collapsing is remote due to the utilization of only oneline riser as compared to twelve or more with a parachute used as aflexible membrane.

It is therefore an object of the present invention to provide aprojectile recovery system which allows relatively low decelerationloads upon impact.

Another object is the provision of a projectile recovery system which isattached to and launched with the projectile.

Still another object is to provide a projectile recovery systemutilizing a ballute drag device and only one line riser.

A further object is the provision of a projectile recovery systemutilizing a ballute packaged inside the projectile.

The above objects as well as others together with the benefits andadvantages of the invention will be apparent upon reference to thedetailed description set forth below, particularly when taken inconjunction wit-h the drawings annexed hereto:

FIG. 1 shows a partial sectional view of the present invention.

FIG. 2 illustrates an operational three stage view of the presentinvention.

As seen in FIG. 1, the payload recovery system 10 includes a projectilebody assembly 12 and a recovery assembly 14. The recovery assembly 14comprises a hollow cylinder 16 and a propelling yoke 18. The cylinder 16is retained on the propelling yoke 18 by a series of pins 20.

A ballute drag device 22 is located inside of cylinder 16 and propellingyoke 18 and is attached by a single line riser 24 to a thrust bearing25. A ballute is defined as a drag device which acts similar to both aballoon and a parachute.

A member 26 is positioned to cover a pair of adjacent bearings 28. Aholder bearing 30 is positioned through the center of said bearings 28having male screw threads 32 for securing to the female screw threads 34of plate 36. A pair of dowel pins 38 extend from said holder hearing 30into said plate 36 for further security. Secured to said cover member 26by cup-point set screws 40 is a swivel plate 42. Four shear pins 44(only two are shown) are secured to said plate 36', apart around thecircumference of said plate 36. Secured inside said propelling yoke 18on opposite sides of the bearings 28 are a pair of pistons 46, eachpiston having an O ring 48 located in groove 50 and a spring 52. Thesprings 52 are utilized to give an additional boost to said yoke 18after initiation of said yoke 18 away from said payload. The pistons 46are restricted during their thrust stroke by screws 51.

At the front of the propelling yoke 18 of the recovery assembly 14 is afuze 54, which can be for example a mechanical time fuze,resistance-capacitance type, an electronic type, barometric type, etc.Located at the rear of the fuze 54 is a propellent case 56 having aninitiating device 58, i.e. primer, detonation, etc., and propellent 60,therein. The activated fuze 54 releases the initiating device 58 at apredetermined time. This device 58 ignites the propellent 60.

The acceleration force activates a release mechanism (not shown) in thefuze 54. The acceleration function 15 where a=acceleration Gs P=Chamberpressure in pounds per inches 2 A|=Bore area in inches 2 W=Weight ofprojectile in pounds In operation, the drag device 22 is packaged aspart of the projectile body 12 to be recovered. The payload recoverysystem 10 is launched (see FIG. 2) by a launcher 62, during thelaunching environment a fuzin-g mechanism 54 is activated which allowsthe recovery system 10 to reach a predetermined height at which time thefuzing mechanism initiates a propellent 60. The propellent 60 burns andgenerates gas which causes separation of the cylinder 16 which surroundsthe drag device 22 by generating enough pressure to break the shear pins44 there by allowing the springs 54 to lift the yoke 18 away from thepayload. The drag device 22 which is retained to the projectile body 12through a thrust type bearing 28 is then subject to dynamic pressure.The dynamic pressure inflates the drag device 22. The spin of theprojectile (as shownrrby the arrows in FIG. 2) is segregated from thedrag device 22 by the aforementioned thrusttype bearing. After the dragdevice 22 is inflated, the high drag force of the drag device 22 retardsthe projectile velocity and orientates the projectile 12 with respect tothe ground causing relatively light impact of the projectile 12 with theground. The drag force generated by the ballute drag device 22 forcesthe projectile 12 to assume an orientation in the direction of gravityand also restricts the free fall of the projectile 12.

The system can also be launched without a timing system. Under thiscondition the cylinder 16 containing the drag device 22 is separteed bythe drag force.

When the drag force on the cylinder 16 is large enough to cause adiflierence in acceleration between the projectile body 12 and thecylinder 16, the cylinder 16 is forced from the body 12 through theaction of springs 52 allowing the drag device 22 to be inflated with ramair.

In inflating the drag device 22, the surrounding dynamic pressure isforced into the side inlets 64. Upon inflation, the projectile body 12begins its fall, (FIG. 2), when the single line riser is fully extendedthe balluate drag device allows the descent of the projectile body 12allowing for a minimum G load landing or a mid-air pick up by anairborne vehicle.

Obviously many modifications and variations of the present invention arepossible in light of the above teachings. -It is therefore to beunderstood, that within the scope of the appended claims, the inventionmay be practiced otherwise than as specifically described.

I claim:

1. A payload recovery system comprising,

a hollow cylindrical body,

-a payload attached at the rearward end of said body,

a balluatedevice located within said body,

a thrust bearing securing said ballute device to said payload andincluding,

a pair of adjacent barings,

a cover member attached to said bearings,

a holder bearing extending through the center of said bearings, andhaving male screw threads,

a plate adjacent said holder bearing, having female screw threads forreceiving said male screw threads of said holder bearing, and

means attached tothe forward end of said body, for separating said bodyfrom said payload at a predetermined time after activation including, afuse, a propellant case located at the rearward end of said .fuse,containing initiating means and a propellant therein, a pair of dowelpins extending from said holder bearing into said plate,

a plurality of shear .pins secured to said plate,

a swivel plate secured to said cover member by a plurality of cup pointset screws,

a propelling yoke located inside said hollow cylindrical body,

a plurality of pins maintaining said body on said yoke,

a plurality of pistons secured inside said yoke and located on oppositesides of said bearing, and

an O ring and a spring provided adjacent and in contact with one end ofsaid piston.

2. A system of the type described in claim 1, wherein ballute device isconnected to said cover by a single line user.

3. A system of the type described in claim 2, including a plurality ofair inlets located on said ballute device in such a manner as saidballute will be inflated by ram air.

4. A system of the type described in claim 3, wherein said pistons havegrooves thereon,

said 0 rings being located in said grooves, and

said spring means are located at the end port-ion of each piston.

References Cited UNITED STATES PATENTS 1,309,982 7/ 1919 Darling .a10235.6 1,624,837 4/ 1927 Holmes 308- 1,978,641 10/1934 Martin 10235.62,342,096 2/ 1944 Zimmerman 102-35.6 2,616,369 111/1952 Brown 102-4X2,828,690 4/ 1-958 Freri 10235 3,038,407 6/1962 Robertson et a1.102-35.4 X 3,168,266 2/:1965 Yost 244-138 W. KUJAWA, Assistant Examiner.

